Advanced Scramjet Engine/Vehicle Design
Department of Defense
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Small Business Information
Combustion Research and Flow Technology,
6210 Kellers Church Road, Pipersville, PA, -
Socially and Economically Disadvantaged:
AbstractThe program focuses on the development of a unified design and optimization framework for hypersonic scramjet propulsive flowpaths. Preliminary design tools utilizing inverse ray tracing and characteristic techniques, as well as CFD codes containing advanced turbulence and chemical kinetic models are incorporated. The end-to-end design framework starts with basic user-defined parameters such as the combustor/isolator shape and cross-section and proceeds systematically from inlet to combustor to nozzle, recognizing that the realistic profiles from one component have a first-order effect on the performance of the subsequent component. The framework considers transitional effects and the design of trips, scalar fluctuation effects on mixing/combustion efficiency, and detailed ignition and recombination chemical kinetics in the combustor and nozzle. The framework will be used to design a hydrogen-fueled, Mach 10 inward-turning propulsive flowpath for a design having an elliptical cross-section combustor. Inlet design will address leading edge effects and crotch design will emphasize self-starting issues. The combustor design will use flush-mounted injectors with optimized spacing and fuel/airstream momentum ratios. Nozzle design will address propulsive performance as well as lift augmentation. Innovative concepts to be considered in this design include transpiration cooling, injection of nano Al, fluidic transitional trips, and base burning.
* information listed above is at the time of submission.